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公开(公告)号：US11851217B1
公开(公告)日：2023-12-26
申请号：US16745725
申请日：2020-01-17
Applicant: Ball Aerospace & Technologies Corp.
Inventor： Emil Tchilian , Zachary Schmidt , Bevan D. Staple
IPC: B64G1/00 , B64G1/36 , G01S3/786 , G06T5/00 , G06T7/246 , G06N3/08 , G06N3/04 , G06V10/40 , G06F18/214 , H04N23/54 , H04N23/55
CPC classification number: B64G1/361 , G01S3/7867 , G06F18/214 , G06N3/04 , G06N3/08 , G06T5/002 , G06T7/246 , G06V10/40 , H04N23/54 , H04N23/55 , G06T2207/20081 , G06T2207/20084
Abstract: Star tracker systems and methods are provided. The star tracker incorporates deep learning processes in combination with relatively low cost hardware components to provide moderate (e.g. ˜1 arc second attitude uncertainty) accuracy. The neural network implementing the deep learning processes can include a Hinton's capsule network or a coordinate convolution layer to maintain spatial relationships between features in images encompassing a plurality of features. The hardware components can be configured to collect a blurred or defocused image in which point sources of light appear as blurs, and in which the blurs create points of intersection. Alternatively or in addition, a blurred or defocused image can be created using processes implemented as part of application programming. The processing of collected images by a neural network to provide an attitude determination can include analyzing a plurality of blurs and blur intersections across an entire frame of image data.
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公开(公告)号：US20230286675A1
公开(公告)日：2023-09-14
申请号：US18118720
申请日：2023-03-07
Applicant: The Government of the United States of America, as represented by the Secretary of the Navy
Inventor： Evan M. Ward , Bryan C. Brown , David F. Chicka , Nathaniel K. Ng
CPC classification number: B64G1/244 , B64G1/361 , B64G1/365 , G06T7/11 , B64G2001/247
Abstract: Systems and methods are provided for high fidelity long-duration autonomous spacecraft navigation relative to a planet's surface and measuring the dynamics of the planet. For a planet like Earth, embodiments of the present disclosure can be used to estimate the unpredictable components of Earth's orientation with respect to the inertial frame. Embodiments of the present disclosure further enable autonomous landmark navigation by providing systems and methods for satellites to autonomously recognize landmarks, using, for example, multiple computer vision approaches to recognize multiple types of landmarks.
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3.发明申请TORQUE GENERATION SYSTEM, ATTITUDE CONTROL SYSTEM FOR SPACECRAFT, AND RELATIVE POSITION AND VELOCITY CONTROL SYSTEM FOR SPACECRAFT 审中-公开扭矩发生系统，空间姿态控制系统及相关位置及速度控制系统公开(公告)号：US20160376032A1
公开(公告)日：2016-12-29
申请号：US15150994
申请日：2016-05-10
Applicant: Japan Aerospace Exploration Agency
Inventor： Osamu MORI , Junichiro KAWAGUCHI , Yoji SHIRASAWA , Toshihiro CHUJO , Kosuke AKATSUKA
CPC classification number: B64G1/407 , B64G1/10 , B64G1/24 , B64G1/34 , B64G1/36 , B64G1/361 , B64G1/365 , B64G1/44 , B64G1/443 , H02S40/30
Abstract: A torque generation system includes: a plurality of solar array panels and/or solar array panel divisions; and a torque controller configured to control an electricity generation ratio of each of the plurality of solar array panels and/or solar array panel divisions to generate torque.
Abstract translation: 扭矩产生系统包括：多个太阳能阵列面板和/或太阳能阵列面板部分; 以及转矩控制器，其被配置为控制所述多个太阳能电池阵列面板和/或太阳能电池阵列面板部分中的每一个的发电率以产生转矩。
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公开(公告)号：US09296495B2
公开(公告)日：2016-03-29
申请号：US14454162
申请日：2014-08-07
Applicant: Jena Optronik GmbH
Inventor： Rolf Hartmann , Dieter Schoedlbauer , Uwe Schmidt
Abstract: A hybrid network of kinematic sensors of an AOCS, made up of a star sensor including an optical camera head, and a processing unit provided as the central master processing unit, and additional kinematic sensors, each made up of a sensor element and a processing unit connected to the central processing unit via a first bus. An additional processing unit is equivalent to the processing unit and is a redundant central processing unit. The central processing units and—are connected via an additional bus of a spacecraft provided with the hybrid network with the aid of a central computer. The particular active central processing units-provide all kinematic sensors with a uniform time pulse via a synchronization line, and supply the central computer with hybridized kinematic measuring data formed according to a method for hybridization based on the synchronous kinematic measuring data of the star sensor and the measuring data of the other sensors.
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5.发明申请METHODS AND APPARATUS FOR PERFORMING PROPULSION OPERATIONS USING ELECTRIC PROPULSION SYSTEMS 有权使用电动推进系统执行推进操作的方法和装置公开(公告)号：US20160046394A1
公开(公告)日：2016-02-18
申请号：US14828462
申请日：2015-08-17
Applicant: The Boeing Company
Inventor： James J. Peterka, III , Glenn N. Caplin , Richard W. Aston
CPC classification number: B64G1/242 , B64G1/002 , B64G1/007 , B64G1/10 , B64G1/26 , B64G1/283 , B64G1/361 , B64G1/363 , B64G1/365 , B64G1/40 , B64G1/402 , B64G1/405 , B64G1/422 , B64G1/428 , B64G1/44 , B64G1/503 , B64G1/641 , B64G2001/643
Abstract: Methods and apparatus to methods and apparatus for performing propulsion operations using electric propulsion system are disclosed. An example method includes deploying a space vehicle including an electric propulsion system; and using the electric propulsion system for attitude control and orbit control, no other propulsion system provided to enable the attitude control and the orbit control.
Abstract translation: 公开了使用电推进系统执行推进操作的方法和装置的方法和装置。 示例性方法包括部署包括电推进系统的空间车辆; 并采用电动推进系统进行姿态控制和轨道控制，无需提供其他推进系统，实现姿态控制和轨道控制。
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Patent Agency Ranking
6.发明申请公开(公告)号：US20150369607A1
公开(公告)日：2015-12-24
申请号：US14309324
申请日：2014-06-19
Applicant: The Boeing Company
Inventor： Ryan Jirapong , David D. Needelman , Bradley W. Taylor , Patrick J. Moran , Michael G. Novean
CPC classification number: G01C21/025 , B64G1/361 , B64G2001/245 , G01C25/00 , G06F17/30241
Abstract: A system and method for mitigating an occurrence of a dry spot, the method may include: (1) predicting the occurrence of the dry spot by at least one of determining a location of the occurrence of the dry spot, determining a date of the occurrence of the dry spot, and determining a duration of the occurrence of the dry spot; (2) generating a visualization of the occurrence of the dry spot, and (3) modifying a star catalog to reduce an impact of the dry spot by at least one of generating a set of modification to modify the star catalog, generating a modification schedule for modifying the star catalog, and uploading the set of modifications to the star catalog.
Abstract translation: 一种用于减轻干点发生的系统和方法，所述方法可以包括：（1）通过确定干点发生的位置，确定发生日期的至少一个来预测干斑的发生 的干点，并确定干点发生的持续时间; （2）产生干点发生的可视化，以及（3）通过生成一组修改以修改星号目录中的至少一个来修改星号目录以减少干点的影响，生成修改时间表 用于修改星号目录，并将修改集上传到星号目录。
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公开(公告)号：US09108748B2
公开(公告)日：2015-08-18
申请号：US12925386
申请日：2010-10-20
Applicant: Saghir Munir , Darren Stratemeier , Xen Price , Yassir Azziz , Jorge Delgado , Justo Jacinto
Inventor： Saghir Munir , Darren Stratemeier , Xen Price , Yassir Azziz , Jorge Delgado , Justo Jacinto
Abstract: Apparatus and methods for raising the orbit of a satellite having electric propulsion thrusters, an Earth sensor and an inertial reference sensor such as a gyro. A satellite positioning system generates orbital data and a profile generator generates an ideal electric orbit raising profile of the satellite. The ideal profile is one that the satellite must follow so that the perigee, apogee and inclination of the satellite can be adjusted simultaneously in a mass-efficient manner. A state machine processes the ideal profile and a true anomaly to generate a desired electric orbit raising profile. Steering apparatus generates signals that are used to control the attitude of the satellite to follow the desired profile. The desired profile places the satellite in an Earth-pointed attitude when the satellite is at a predefined point in the orbit, slews the satellite from the Earth-pointed attitude to an ideal orbit raising attitude, steers the satellite according to the ideal profile during orbit raising, and steers the satellite from the desired attitude to the Earth-pointed attitude.
Abstract translation: 用于升高具有电力推进推进器的卫星的轨道的装置和方法，地球传感器和诸如陀螺仪的惯性参考传感器。 卫星定位系统产生轨道数据，轮廓发生器产生卫星的理想的电轨道升高轮廓。 理想的配置是卫星必须遵循的，以便能够以高效率的方式同时调整卫星的近地点，远地点和倾斜度。 状态机处理理想轮廓和真实异常以产生期望的电轨道提升轮廓。 转向装置产生用于控制卫星遵循所需轮廓的姿态的信号。 当卫星在轨道上的预定义点处时，所需的轮廓将卫星置于地球姿态，将卫星从地面倾斜姿态转换为理想的轨道提升姿态，在卫星轨道上根据理想轮廓引导卫星 将卫星从理想的态度引导到地球尖锐的态度。
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公开(公告)号：US20150115107A1
公开(公告)日：2015-04-30
申请号：US14064226
申请日：2013-10-28
Applicant: Fukashi Andoh
Inventor： Fukashi Andoh
CPC classification number: B64G1/1078 , B64G1/242 , B64G1/26 , B64G1/361 , B64G1/645 , B64G1/646 , B64G1/66 , B64G2001/245
Abstract: A space debris remover aiming to remove a space debris object in earth orbits. Angular thrust calculation unit calculates angular thrust. Radial thrust calculation unit calculates radial thrust based on the angular thrust, estimated angular momentum and estimated space debris mass. A foam bonding mechanism connects the space debris remover and the space debris object. A space debris removal controller calculates firing time, and sends a space debris removal control signal comprising the radial thrust, the angular thrust and the firing time. A plurality of first stage thrusters generate the radial thrust and the angular thrust after the firing time. After the stage separator separates a first stage and a second stage of the space debris remover, a plurality of second stage thrusters generate the radial thrust and the angular thrust, and propel the space debris object towards the sun.
Abstract translation: 旨在消除地球轨道上的空间碎片物体的空间碎片清除装置。 角推力计算单元计算角度推力。 径向推力计算单元基于角推力，估计角动量和估计的空间碎片质量来计算径向推力。 泡沫粘合机构连接空间碎片清除器和空间碎片物体。 空间碎片清除控制器计算点火时间，并发送包括径向推力，角度推力和燃烧时间的空间碎片去除控制信号。 多个第一级推进器在点火时间之后产生径向推力和角推力。 在舞台分离器分离空间碎片去除器的第一阶段和第二阶段之后，多个第二阶段推进器产生径向推力和角度推力，并将空间碎片物体推向太阳。
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公开(公告)号：US08868263B2
公开(公告)日：2014-10-21
申请号：US13115370
申请日：2011-05-25
Applicant: Mohammad Saghir Munir , John Hutton Cooper , Philip Conway Hirschberg
Inventor： Mohammad Saghir Munir , John Hutton Cooper , Philip Conway Hirschberg
CPC classification number: G05D1/0883 , B64G1/24 , B64G1/26 , B64G1/283 , B64G1/361 , B64G1/365 , B64G1/405 , B64G1/407 , B64G1/44
Abstract: Stored momentum on a spacecraft is managed by determining a target profile of stored momentum as a function of time for the spacecraft; measuring a difference between a momentum value actually stored on the spacecraft and a desired momentum value, where the desired momentum value substantially conforms to the target profile at a particular time; reducing the difference by producing a torque on the spacecraft, where the torque results from selectively controlling at least one solar array position offset angle, the offset angle being an offset of at least one solar array of the spacecraft from a nominal sun pointing direction.
Abstract translation: 通过确定作为航天器时间的函数的存储动量的目标轮廓来管理航天器上的存储动量; 测量实际存储在航天器上的动量值与期望动量值之间的差异，其中期望动量值在特定时间基本上符合目标轮廓; 通过在航天器上产生扭矩来减小差异，其中扭矩由选择性地控制至少一个太阳能阵列位置偏移角度而产生，该偏移角度是航天器的至少一个太阳能阵列与标称太阳指向方向的偏移。
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公开(公告)号：US20140236401A1
公开(公告)日：2014-08-21
申请号：US14181504
申请日：2014-02-14
Applicant: The Boeing Company
Inventor： Tung-Ching Tsao , Richard Y. Chiang
Abstract: An attitude estimator that uses star tracker measurements and enhanced Kalman filtering, with or without attitude data, to provide three-axis rate estimates. The enhanced Kalman filtering comprises taking an average of forward and rearward propagations of the Kalman filter states and the error covariances. The star tracker-based rate estimates can be used to control the attitude of a satellite or to calibrate a sensor, such as a gyroscope.
Abstract translation: 一种使用星形跟踪测量和增强卡尔曼滤波的姿态估计器，具有或不具有姿态数据，以提供三轴速率估计。 增强卡尔曼滤波包括对卡尔曼滤波器状态和误差协方差的前向和后向传播的平均值。 基于星座跟踪器的速率估计可用于控制卫星的姿态或校准诸如陀螺仪的传感器。
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